Effect Of Micro-vortex Generator In Hypersonic Inlet. Hypersonic Intake Optimization Using Computational Fluid Dynamics [CFD]

      Аннотация: The recent advances in aerospace vehicle technology demands the best possible propulsive balance to provide better thrust and minimum drag. Air-breathing engines are the best choice for the propulsion due to its minimum weight. The efficiency of such engines depend upon the quality of air entering for combustion. This book provides complete flow analysis of both pure inline-compression and mixed-compression inlets. Two dimensional simulations were carried out with SST k-? model using FLUENT. The boundary layer formed inner side of the engine had an adverse pressure gradient on the ramp producing a boundary layer separation. Due to this the boundary layer thickens and the static pressure starts to decrease whose effect leads till the trailing edge of inlet. Small wedge shaped Micro-Vortex Generator (MVG) inside the inlet smoothen the generated shock-boundary layers and thereby an efficient compression is obtained . The analysis should help shed some light on hypersonic inlet design optimization at off-design condition and should be especially useful to researchers and academicians in the field of Aerospace Engineering.

Ключевые слова: Computational fluid dynamics, CFD, Micro-vortex generator, MVG, MACH NUMBER, Hypersonic Inlet, SCRAM Jet Engine, Supersonic Combustion Ramjet Engine